mearth = 5.9742 x 1024 kg
rearth = 6.3781 x 106 m
mmoon = 7.36 x 1022 kg
rmoon = 1.7374 x 106 m
dearth to moon = 3.844 x 108 m (center tocenter)
G = 6.67428 x 10-11 N-m2/kg2
A 1900 kg satellite is orbitting the earth in a circular orbitwith an altitude of 1500 km.
1) How much energy does it take just to get it to this altitude?2.26*10^10 J
2) How much kinetic energy does it have once it has reached thisaltitude? 4.81*10^10 J
3) What is the ratio of the this change in potential energy tothe change in kinetic energy? (i.e. what is (a)/(b)?)0.47
4) What would this ratio be if the final altitude of thesatellite were 4200 km?
5) What would this ratio be if the final altitude of thesatellite were 3185 km?
